CN110682751B - Mechanism for assisting aircraft to land and water slide based on water-beating float principle - Google Patents
Mechanism for assisting aircraft to land and water slide based on water-beating float principle Download PDFInfo
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- CN110682751B CN110682751B CN201910988137.5A CN201910988137A CN110682751B CN 110682751 B CN110682751 B CN 110682751B CN 201910988137 A CN201910988137 A CN 201910988137A CN 110682751 B CN110682751 B CN 110682751B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
- B60F3/00—Amphibious vehicles, i.e. vehicles capable of travelling both on land and on water; Land vehicles capable of travelling under water
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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Abstract
The invention relates to the field of amphibious aircraft taxiing mechanisms, in particular to a mechanism for assisting an aircraft in taxiing on the basis of a water-beating float principle. Comprises a front sliding mechanism part and a rear sliding mechanism part; the front sliding mechanism part is arranged at the nose landing gear and comprises a nose landing gear riding plate, a nose landing gear body support, a nose landing gear wheel, a nose landing gear riding plate fixing support, a nose landing gear hydraulic buffer actuating cylinder, a nose landing gear bolt and a connecting section hydraulic buffer; the rear sliding mechanism part is arranged at the rear landing gear and comprises a rear landing gear body support, a rear landing gear riding plate, a rear landing gear tail rudder, a rear landing gear hydraulic buffer actuating cylinder, a rear landing gear wheel support, a rear landing gear wheel and a rear landing gear bolt. The invention can make the aircraft take off in the ground, improve the flight height, widen the detection range, reduce the water surface resistance, and do not need the engine to provide excessive power.
Description
Technical Field
The invention relates to the field of amphibious aircraft taxiing mechanisms, in particular to a mechanism for assisting an aircraft in taxiing on the basis of a water-beating float principle.
Background
With the continuous development of aircraft technology, the human beings have satisfied the aircraft not only travel in the air and run on the ground, but also expanded the "hunting" range of the aircraft into water. The amphibious aircraft is mainly used in the environments of oceans, rivers and lakes, can be influenced by wind power and sea waves in the processes of water planing and taking off and landing, has the combined action of aerodynamic force and hydrodynamic force, and not only fully considers the aerodynamic layout and the hydrodynamic layout in the overall design, but also pays more attention to the matching and coordination between the aerodynamic layout and the hydrodynamic layout. The lift-increasing and drag-reducing are the keys for ensuring the short-distance take-off and landing capability of the water surface and good low-altitude low-speed flight performance.
Because the take-off and landing of the aircraft on water and land are generally realized by arranging a ship-shaped fuselage and stabilizing the whole two-side streamline auxiliary devices. The design of the ship-shaped fuselage enables the amphibious aircraft to generate enough buoyancy when sliding on the water surface and the streamlined hull can reduce the resistance of water. However, for offshore exploration aircraft, the aircraft is required to perform tasks close to the sea surface, the aircraft with a ship-shaped fuselage must be powered by the engine when taxiing on the water, and a larger ship shape necessarily results in less taxiing resistance and requires more energy to be consumed by the engine. The three-point type landing gear is arranged, the front landing gear is provided with a riding plate with a proper size (the airplane wheels are hidden above the riding plate), floating sliding on the water surface is realized in a 'water-floating' mode, the rear landing gear is provided with a small ship type support and is stable (the airplane wheels are hidden in a ship type machine body), and the tail part is provided with a tail rudder for assisting steering and cooperating with the front landing gear to realize 'micro-power' sliding on the water surface. Therefore, the resistance in floating and sliding can be greatly reduced, excessive power is not required to be provided by an engine, and energy is saved. The ship-shaped fuselage and the front three-point undercarriage are adopted to assist in the design of the riding plate, and the optimization of pneumatic, hydrodynamic and structural integration is realized, so that the structure weight can be reduced, the pneumatic efficiency is improved, and the ship-shaped fuselage and the front three-point undercarriage are more suitable for the water environment. The key technology of taking off and landing of the amphibious aircraft lies in the design of the landing gear. The landing gear of the amphibious aircraft has different requirements from the traditional aircraft, and not only can be used for sliding and taking off and landing on land, but also can be folded to reduce resistance when the aircraft is on the water surface.
At present, most amphibious aircrafts are gyroplanes, the flying height is very limited, the requirement on a power system is high, but if the amphibious function of the aircraft is realized only by an engine, more fuel must be carried, so that the weight of the aircraft is increased, and the service life of the engine is shortened. In order to solve the problem, a mechanism for assisting the aircraft in amphibious gliding based on the principle of 'water-beating-floating' is provided, and the mechanism is used for the fixed-wing amphibious aircraft, so that the fixed-wing amphibious aircraft can glide and take off on the ground, and the gliding resistance is reduced when the fixed-wing amphibious aircraft glides on the water surface to execute related tasks.
Disclosure of Invention
The invention aims to provide a mechanism for assisting an aircraft in land-water taxiing based on a water-beating-drift principle, which can take off on the ground in a sliding manner, improve the flying height of the aircraft, widen the detection range of the aircraft, reduce the water surface sliding resistance of the aircraft, and does not need an engine to provide excessive power.
The purpose of the invention is realized by the following steps:
a mechanism for assisting an aircraft in land and water sliding based on a water beating and floating principle comprises a front sliding mechanism part and a rear sliding mechanism part; the front sliding mechanism part is arranged at the front landing gear and connected to the body; the rear slide mechanism is partially mounted at the rear landing gear and is connected to the fuselage.
The invention also comprises the following structural features:
1. the front sliding mechanism part comprises: the nose landing gear comprises a nose landing gear riding plate 1, a nose landing gear body support 2, a nose landing gear wheel support 3, a nose landing gear wheel 4, a nose landing gear riding plate fixing support 5, a nose landing gear hydraulic buffer actuating cylinder 6, a nose landing gear bolt 7 and a connecting section hydraulic buffer 8; the front landing gear riding plate 1 is of a two-piece rectangular curved surface smooth plate structure and is symmetrically distributed on the left side and the right side of the bottom end of the front sliding mechanism part, and the upper end of the front landing gear riding plate 1 is connected with a front landing gear riding plate fixing support 5 and a front landing gear hydraulic buffer actuating cylinder 6 through bolts; the nose landing gear body support 2 is of a supporting rod structure, the upper end of the nose landing gear body support is connected with the axial truss of the nose landing gear body through a bolt, the middle upper part of the nose landing gear body support 2 is connected with the lower end of a hydraulic buffer 8 of a connecting section, the middle lower part of the nose landing gear body support 2 is connected with a nose landing gear hydraulic buffer actuating cylinder 6, and the lower end of the nose landing gear body support 2 is connected with a nose landing gear wheel support 3; the nose landing gear wheel support 3 is of a support rod structure, the middle part of the nose landing gear wheel support is fixedly connected with the center of a nose landing gear riding plate fixing support 5, and the lower end of the nose landing gear wheel support 3 is connected with a nose landing gear wheel 4 through a bearing; the hydraulic buffer actuating cylinder 6 of the nose landing gear is of three hydraulic buffer structures, and the middle and the left and right sides of the hydraulic buffer actuating cylinder are respectively connected with a nose landing gear body support 2, a nose landing gear riding plate fixing support 5 and a nose landing gear bolt 7; the hydraulic buffer 8 at the connecting section is a hydraulic buffer structure, and the upper end of the hydraulic buffer is connected with the axial truss of the same machine body through a bolt.
2. The rear slide mechanism portion includes: a rear landing gear body support 9, a rear landing gear riding plate 10, a rear landing gear tail rudder 11, a rear landing gear hydraulic buffer actuator cylinder 12, a rear landing gear wheel support 13, a rear landing gear wheel 14 and a rear landing gear bolt 15; the rear landing gear body support 9 is of two support plate structures which are symmetrically distributed on the left side and the right side of the rear landing gear mechanism part in an A shape, the upper end of the rear landing gear body support 9 is connected with hinge holes reserved on the two sides of the body through rear landing gear bolts 15, a support rod is arranged in the middle of the rear landing gear body support 9 to connect the two support plates with each other, and the lower end of the rear landing gear body support 9 is connected in the middle of the rear landing gear riding plate 10; the rear landing gear riding plate 10 is of a streamline smooth plate structure which is flat at the top and curved at the bottom, sharp at the front and flat at the back and is symmetrically distributed at the left side and the right side of the rear sliding mechanism part, the middle part of the rear landing gear riding plate 10 is of an open cavity structure, and the tail part of the rear landing gear riding plate 10 is connected with a rear landing gear tail rudder 11; the hydraulic buffer actuating cylinder 12 of the rear landing gear is of a hydraulic buffer structure, is positioned in a cavity of an opening in the middle of the riding board 10 of the rear landing gear, and one end of the hydraulic buffer actuating cylinder is connected with a wheel support 13 of the rear landing gear; the rear landing gear wheel 14 is connected to the lower end of the rear landing gear wheel support 13 by a bearing.
3. The front landing gear hydraulic buffer actuating cylinder 6 and the rear landing gear hydraulic buffer actuating cylinder 12 activate retraction and release in the takeoff and landing stage of the aircraft and simultaneously relieve impact load;
4. the front landing gear riding plate 1 and the rear landing gear riding plate 10 are both of hollow structures;
5. the hydraulic buffer actuating cylinder 6 of the nose landing gear can change the angle between the nose landing gear riding plate 1 and the water surface.
The invention has the beneficial effects that:
1. the interior of the sliding mechanism is hollow, so that the weight of the whole sliding mechanism is effectively reduced, the wheels of the rear landing gear are hidden in the riding board of the rear landing gear, the navigation resistance can be reduced, the streamline structure of the riding board is not damaged, and the resistance in the sliding process is effectively reduced;
2. when the aircraft slides on the water surface, the front landing gear wheels and the rear landing gear wheels are all arranged in the sliding mechanism, so that the resistance in the sliding process is effectively reduced by the front landing gear riding plate and the rear landing gear riding plate when the aircraft slides on the water surface, and the rear landing gear tail rudder is arranged on the rear bearing plate in the sliding process, so that the direction can be better controlled, the turning is more flexible, the steering resistance is reduced, and free sliding is realized;
3. when the invention is applied to the fixed-wing amphibious aircraft, the fixed-wing amphibious aircraft can take off on the ground in a sliding manner, thereby improving the flight height of the aircraft and enlarging the detection range; when the aircraft slides on the water surface to execute related tasks, the mechanism can reduce the resistance during sliding, is flexible in steering, does not need an engine to provide excessive power, and has a very large application prospect;
drawings
FIG. 1 is an overall block diagram of the nose landing gear of the present invention in a planing attitude on the water;
FIG. 2 is an enlarged partial structural view of the nose landing gear of the present invention in a planing attitude on the water;
FIG. 3 is an overall block diagram of the nose landing gear of the present invention in a planing attitude on land;
FIG. 4 is an overall block diagram of the rear landing gear of the present invention in a planing attitude on the water;
FIG. 5 is an overall block diagram of the rear landing gear of the present invention in a planing on land attitude.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, the present invention is further described with reference to the accompanying drawings:
the reference numbers in the figures are: the nose landing gear comprises a nose landing gear riding plate 1, a nose landing gear body support 2, a nose landing gear wheel support 3, a nose landing gear wheel 4, a nose landing gear riding plate fixing support 5, a nose landing gear hydraulic buffer actuating cylinder 6, a nose landing gear bolt 7, a connecting section hydraulic buffer 8, a rear landing gear body support 9, a rear landing gear riding plate 10, a rear landing gear tail rudder 11, a rear landing gear hydraulic buffer actuating cylinder 12, a rear landing gear wheel support 13, a rear landing gear wheel 14 and a rear landing gear bolt 15.
The technical scheme of the invention is realized as follows:
the design discloses an amphibious sliding mechanism. The specific structure is shown in fig. 1 and fig. 2, and the main structure is as follows: 1-riding plate, 2-airplane body support, 3-airplane wheel support, 4-front airplane wheel, 5-riding plate fixing support (fixedly connected with 3-airplane wheel support), 6-hydraulic buffer actuating cylinder, 7-bolt, 8-connecting section hydraulic buffer, 9-airplane body support, 10-riding plate, 11-tail rudder, 12-hydraulic buffer actuating cylinder, 13-airplane wheel support, 11-rear airplane wheel and 15-connecting bolt. The working principle of the mechanism is as follows: when the aircraft takes off or lands and slides on the land, the front mechanism 1-riding board end is retracted through the 6-hydraulic buffer actuating cylinder, and the rear mechanism 11-hydraulic buffer actuating cylinder is put down, so that the states of the right side of the figure 1 and the left side of the figure 2 are formed. The front mechanism middle section 6-hydraulic buffer actuating cylinder and the rear mechanism middle section 12-hydraulic buffer actuating cylinder can relieve impact load during landing. When the airplane slides on the water surface or the 'water float', the front mechanism 1-riding plate end is put down through the 6-hydraulic buffer actuating cylinder, the rear mechanism 12-hydraulic buffer actuating cylinder is put away, and the rear wheel is hidden in the rear riding plate to form the working states of the left side of the figure 1 and the right side of the figure 2. The rear wheels are hidden in the rear riding plate, so that the sailing resistance can be reduced, and the streamline structure of the riding plate is not damaged. The rear carrier plate is provided with 11-tail rudders for better control of direction and more flexible turning. The nose landing gear of the mechanism is hinged through a 15-connecting bolt, a 2-body connecting support and an 8-connecting hydraulic buffer are jointly connected to the same axial truss of the body, and the rear landing gear is hinged through a 15-connecting bolt through hinge holes reserved on two sides of the body.
When the unmanned aerial vehicle slides on the land, the front and rear sliding mechanisms are supposed to take off through the sliding of the airplane wheels like the landing gear of the airplane; when the 'water-floating' sports and the sliding are carried out on the water, the riding plate structure ensures that the whole machine body does not sink. Based on this idea, a front and a rear skidding mechanisms as shown in fig. 1 and 2 are designed to eject a 4-wheel and a 14-wheel placed inside the skidding mechanism respectively when used for land parking or take-off. To reduce rear deck drag when planing on water, wheels are mounted to the interior of the rear deck. The inside of the sliding mechanism is hollow, so that the weight of the whole machine is effectively reduced. The airplane wheels are retracted and extended by 6-front undercarriage hydraulic buffer actuating cylinders and 12-rear undercarriage hydraulic buffer actuating cylinders. When the unmanned aerial vehicle slides on the water surface, the 4-front airplane wheels and the 14-rear airplane wheels are all arranged in the sliding mechanism, the 1-front riding plate and the 10-rear riding plate can effectively reduce the resistance in the sliding process when the unmanned aerial vehicle slides on the water surface, and the movement direction of the unmanned aerial vehicle can be controlled by the 11-tail vane in the sliding process, so that the steering resistance is reduced, and free sliding is realized.
The specific working process of the device is as follows:
(1) when the unmanned aerial vehicle works on the ground, the 4-airplane wheel and the 14-airplane wheel respectively extend out of the front riding plate and the rear riding plate, so that the unmanned aerial vehicle can slide on the ground to take off and land.
(2) When the unmanned aerial vehicle lands on the water surface, the 6-hydraulic buffer actuating cylinder and the 12-hydraulic buffer actuating cylinder move to realize the retraction and the falling of the frame, so that the frame is respectively positioned above the 1-riding plate and the 10-riding plate; when unmanned aerial vehicle moves on the surface of water, can realize floating the slip on the surface of water through taking advantage of the board around.
(3) When the unmanned aerial vehicle needs to stop in a certain water area, the included angle between the 1-riding plate and the water surface can be changed through the 6-hydraulic buffer actuating cylinder, so that the resistance is increased, and the unmanned aerial vehicle is enabled to be static. And when the water surface needs to be steered, the steering can be flexibly steered by the tail rudder 11 behind the 10-riding plate.
In conclusion, the take-off and landing of the aircraft on water and land are generally realized by arranging a ship-shaped fuselage and stabilizing the whole body by using two side streamline auxiliary devices. The ship-shaped fuselage is designed to enable the amphibious aircraft to generate enough buoyancy when sliding on the water surface, and the streamline ship body can reduce the resistance of water. However, for offshore exploration aircraft, the aircraft is required to perform tasks close to the sea surface, the aircraft with a ship-shaped fuselage must be powered by the engine when taxiing on the water, and a larger ship shape necessarily results in less taxiing resistance and requires more energy to be consumed by the engine. The three-point type landing gear is arranged, the front landing gear is provided with a riding plate with a proper size (the airplane wheels are hidden above the riding plate), floating sliding on the water surface is realized in a 'water-floating' mode, the rear landing gear is provided with a small ship type support and is stable (the airplane wheels are hidden in a ship type machine body), and the tail part is provided with a tail rudder for assisting steering and cooperating with the front landing gear to realize 'micro-power' sliding on the water surface. Therefore, the resistance in floating sliding can be greatly reduced, excessive power is not required to be provided by an engine, and energy is saved.
Claims (5)
1. The utility model provides a mechanism based on beat water and float principle supplementary aircraft land and water slide which characterized in that: comprises a front sliding mechanism part and a rear sliding mechanism part; the front sliding mechanism part is arranged at the front landing gear and connected to the body; the rear sliding mechanism part is arranged at the rear landing gear and connected to the body; the front skid portion comprising: the nose landing gear comprises a nose landing gear riding plate (1), a nose landing gear body support (2), a nose landing gear wheel support (3), a nose landing gear wheel (4), a nose landing gear riding plate fixing support (5), a nose landing gear hydraulic buffer actuating cylinder (6), a nose landing gear bolt (7) and a connecting section hydraulic buffer (8); the front landing gear riding plate (1) is of a two-piece rectangular curved surface smooth plate structure and is symmetrically distributed on the left side and the right side of the bottom end of the front sliding mechanism part, and the upper end of the front landing gear riding plate (1) is connected with a front landing gear riding plate fixing support (5) and a front landing gear hydraulic buffer actuating cylinder (6) through bolts; the nose landing gear body support (2) is of a support rod structure, the upper end of the nose landing gear body support is connected with the axial truss of the nose landing gear body through a bolt, the middle upper part of the nose landing gear body support (2) is connected with the lower end of a connecting section hydraulic buffer (8), the middle lower part of the nose landing gear body support (2) is connected with a nose landing gear hydraulic buffer actuating cylinder (6), and the lower end of the nose landing gear body support (2) is connected with a nose landing gear wheel support (3); the nose landing gear wheel support (3) is of a support rod structure, the middle part of the nose landing gear wheel support is fixedly connected with the center of a nose landing gear riding plate fixing support (5), and the lower end of the nose landing gear wheel support (3) is connected with a nose landing gear wheel (4) through a bearing; the front landing gear hydraulic buffer actuating cylinder (6) is of three hydraulic buffer structures, and the middle part and the left and right sides of the front landing gear hydraulic buffer actuating cylinder are respectively connected with a front landing gear body support (2), a front landing gear riding plate fixing support (5) and a front landing gear bolt (7); the hydraulic buffer (8) of the connecting section is of a hydraulic buffer structure, and the upper end of the hydraulic buffer is connected with the axial truss of the same machine body through bolts.
2. The mechanism for assisting the aircraft in planing water based on the principles of water beating and drifting according to claim 1, wherein: the rear slide mechanism portion includes: the hydraulic buffer device comprises a rear landing gear body support (9), a rear landing gear riding plate (10), a rear landing gear tail rudder (11), a rear landing gear hydraulic buffer actuating cylinder (12), a rear landing gear wheel support (13), a rear landing gear wheel (14) and a rear landing gear bolt (15); the rear landing gear body support (9) is of two support plate structures which are symmetrically distributed on the left side and the right side of the rear landing gear mechanism part in an A shape, the upper end of the rear landing gear body support (9) is connected with hinge holes reserved on the two sides of the body through rear landing gear bolts (15), a support rod is arranged on the inner side of the middle part of the rear landing gear body support (9) to connect the two support plates with each other, and the lower end of the rear landing gear body support (9) is connected in the middle of a rear landing gear riding plate (10); the rear landing gear riding plate (10) is of a streamline smooth plate structure which is flat at the top and curved at the bottom and flat at the front tip and back, and is symmetrically distributed at the left side and the right side of the rear sliding mechanism part, the middle part of the rear landing gear riding plate (10) is of an open cavity structure, and the tail part of the rear landing gear riding plate (10) is connected with a rear landing gear tail rudder (11); the hydraulic buffer actuating cylinder (12) of the rear landing gear is of a hydraulic buffer structure, is positioned in a cavity of an opening in the middle of the riding plate (10) of the rear landing gear, and one end of the hydraulic buffer actuating cylinder is connected with a wheel support (13) of the rear landing gear; the rear landing gear wheel (14) is connected to the lower end of the rear landing gear wheel support (13) by a bearing.
3. The mechanism for assisting the aircraft in planing water based on the principles of water beating and drifting according to claim 1, wherein: the angle between the nose landing gear riding plate (1) and the water surface is changed by the nose landing gear hydraulic buffer actuating cylinder (6).
4. The mechanism for assisting the amphibious aircraft in planing water based on the principles of water-beating and floating as claimed in claim 2, wherein: the front landing gear riding plate (1) and the rear landing gear riding plate (10) are both of hollow structures.
5. The mechanism for assisting the aircraft in planing water based on the principles of water beating and drifting according to claim 2, wherein: the front landing gear hydraulic buffer actuating cylinder (6) and the rear landing gear hydraulic buffer actuating cylinder (12) are activated to be retracted and retracted in the takeoff and landing stage of the aircraft, and impact load is relieved at the same time.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910988137.5A CN110682751B (en) | 2019-10-17 | 2019-10-17 | Mechanism for assisting aircraft to land and water slide based on water-beating float principle |
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| CN201910988137.5A CN110682751B (en) | 2019-10-17 | 2019-10-17 | Mechanism for assisting aircraft to land and water slide based on water-beating float principle |
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| CN111924093A (en) * | 2020-08-18 | 2020-11-13 | 泊鹭（荆门）飞机有限公司 | Amphibious aircraft undercarriage of rotatable formula |
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| CN110682751A (en) | 2020-01-14 |
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